Patent application number | Description | Published |
20080247866 | Compressor and Compressor Housing - A housing is incorporated as part of a compressor having blades that impart to a fluid a momentum along a main gas flow direction and a swirl. The housing includes a channel that has at least one channel wall and defines an axis substantially aligned with the main gas flow direction. The channel is configured to duct at least some of the fluid. The channel wall defines an internal cavity that extends axially within the channel wall. A bleed passage connects and provides fluid communication between the channel and the cavity. The channel wall defines a plurality of injection passages providing fluid communication between the cavity and the channel at a location spaced in a direction opposite the main gas flow direction from both the bleed passage and the blades. The injection passages have a portion configured to direct fluid from the cavity into the channel with a component along the main gas flow direction and a component opposed to the swirl. | 10-09-2008 |
20090293485 | DIFFUSERS, DIFFUSION SYSTEMS, AND METHODS FOR CONTROLLING AIRFLOW THROUGH DIFFUSION SYSTEMS - A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction. | 12-03-2009 |
20100122536 | PLASMA FLOW CONTROLLED DIFFUSER SYSTEM - A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage. | 05-20-2010 |
20130017066 | COMPRESSORS WITH INTEGRATED SECONDARY AIR FLOW SYSTEMSAANM Nolcheff; NickAACI ChandlerAAST AZAACO USAAGP Nolcheff; Nick Chandler AZ USAANM Lee; JongAACI TempeAAST AZAACO USAAGP Lee; Jong Tempe AZ US - A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit. | 01-17-2013 |
20130051974 | GAS TURBINE ENGINES AND METHODS FOR COOLING COMPONENTS THEREOF WITH MID-IMPELLER BLEED COOLING AIR - Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction. | 02-28-2013 |
20140321987 | PLASMA ACTUATED CASCADE FLOW VECTORING - A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary system for directing airflow includes a cascade of internal structures spanning an airflow path. Each of the internal structures includes a rounded trailing edge. The system further includes at least one plasma generating device positioned on the rounded trailing edge of each internal structure. Also, the system includes a controller configured to selectively energize and de-energize each plasma generating device to selectively alter a direction of local airflow around each internal structure to produce a combined airflow exiting the cascade in a desired direction. | 10-30-2014 |
20150030435 | PLASMA FLOW CONTROL INLET PARTICLE SEPARATOR SYSTEM - An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter. | 01-29-2015 |
20150198090 | ELECTROSTATIC CHARGE CONTROL INLET PARTICLE SEPARATOR SYSTEM - An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity. | 07-16-2015 |